CN111288016A - Element blade profile modeling method of axial flow compressor - Google Patents
Element blade profile modeling method of axial flow compressor Download PDFInfo
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- CN111288016A CN111288016A CN201811493691.8A CN201811493691A CN111288016A CN 111288016 A CN111288016 A CN 111288016A CN 201811493691 A CN201811493691 A CN 201811493691A CN 111288016 A CN111288016 A CN 111288016A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F04—POSITIVE - DISPLACEMENT MACHINES FOR LIQUIDS; PUMPS FOR LIQUIDS OR ELASTIC FLUIDS
- F04D—NON-POSITIVE-DISPLACEMENT PUMPS
- F04D29/00—Details, component parts, or accessories
- F04D29/26—Rotors specially for elastic fluids
- F04D29/32—Rotors specially for elastic fluids for axial flow pumps
- F04D29/38—Blades
- F04D29/384—Blades characterised by form
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Abstract
The invention provides a method for modeling an elementary blade profile of an axial flow compressor, which comprises the following steps: s1Obtaining a central streamline of a flow passage enclosed by the adjacent blades according to the camber line profile; s2Obtaining inlet and outlet sections of the flow channel by taking a perpendicular line of the central flow line, and dividing the central flow line between the inlet and outlet sections of the flow channel into n sections; s3Making vertical lines of the central flow line on the dividing points of the two adjacent sections, and respectively taking points on the vertical lines and on the two sides of the central flow line, so that the length of a line segment formed by two points taken on one vertical line is equal to the value of the flow area to be achieved at the position; s4And fitting the points below all the taken central flow lines to form suction surface molded lines, and fitting the points above all the taken central flow lines to form suction surface molded lines. The invention can use the distribution rule of the flow area as modeling input, and designs the blade profile of the gas compressor meeting the requirement of the pre-specified distribution rule of the flow area in a positive and direct way to achieve the flow velocity distribution or shock wave structure.
Description
Technical Field
The invention relates to the field of aero-engines, in particular to a method for modeling an elementary blade profile of an axial flow compressor.
Background
At present, in the field of design of aircraft engines and gas turbines, the main modeling mode of axial flow compressor blades (including fans) is as follows: firstly, designing the basic element blade profile on each blade height section, and then radially stacking the designed basic element blade profiles to form a three-dimensional blade.
Wherein, the modeling method of the primitive leaf profile mainly comprises the following three steps: mean camber line stacking thickness distribution, suction surface stacking pressure surface (including design method of directly giving coordinate point), suction surface stacking thickness distribution, etc.
In the above three element leaf-type modeling methods, the design input mainly includes: camber line profile, blade profile thickness distribution and suction (pressure) surface profile. However, the flow area, as a parameter that is critical to the acceleration and deceleration of the gas in the flow channel (see analysis below), is often the design output and can only be examined after the molding is complete. Therefore, there is no molding method that can input the flow area distribution rule and output the other parameters such as the thickness distribution rule as a molding.
However, the distribution rule of the flow area superimposed by the mean camber line can be found through the calculation of the three-dimensional flow field, and the change of the airflow speed in the flow channel has a very close relation with the change of the flow area. FIG. 1 is a schematic diagram of the results of a three-dimensional CFD calculation, as shown in FIG. 1, with the abscissa representing the dimensionless length of the central flow line, and "0" representing the inlet of the flow channel, and "1" representing the outlet of the flow channel. The left and right vertical coordinates are respectively the central streamline Mach number and the flow passage area of the flow passage. It can be found from fig. 1 that for the example with the outlet back pressure of 12700Pa, the supersonic wave of the incoming flow forms an (oblique) shock wave at the inlet of the flow channel, and the mach number of the wave after the wave is slightly larger than 1, and the supersonic flow still exists. The supersonic airflow is accelerated continuously in the gradually expanding channel with gradually increased flow area until a normal shock wave is formed at the position of about 0.1 dimensionless length, the subsonic airflow decelerates gradually in the gradually expanding channel after wave, the flow area shrinks gradually at the position of about 0.5 dimensionless length, and the subsonic airflow is converted into acceleration to flow out of the flow channel.
For the example with the backpressure of 13300, the incoming flow ultrasonic forms a normal shock wave before entering the flow channel, and the post-wave subsonic flow undergoes a short period of acceleration at the inlet of the flow channel, corresponding to the short period of contraction of the flow area at the inlet of the flow channel. In the subsequent divergent passage, the subsonic flow is maintained in a decelerated flow until, at about 0.5 dimensionless length, the flow area is instead constricted, whereupon the subsonic flow is accelerated until it exits the flow passage. From the above analysis, it can be seen that the acceleration and deceleration in the cascade flow channel are closely related to the change of the flow area, regardless of supersonic or subsonic flows.
Accordingly, the following needs have arisen in the art: whether a modeling method can be designed or not, and a predetermined flow area distribution rule is used as modeling input to carry out blade modeling. The distribution law of the flow area input as the model can be determined according to the distribution law of the air velocity to be realized and the shock wave structure to be realized.
In view of the above, those skilled in the art are devoted to developing a method for modeling the vane profile of the axial compressor element in order to overcome the above problems.
Disclosure of Invention
The invention aims to overcome the defect of limitation of a modeling method of an elementary blade profile in the prior art, and provides a modeling method of an elementary blade profile of an axial flow compressor, which is based on a mean camber line superposition flow area distribution rule.
The invention solves the technical problems through the following technical scheme:
the modeling method of the blade profile of the axial flow compressor element is characterized by comprising the following steps of:
S1obtaining a central streamline of a flow passage enclosed by the adjacent blades according to the camber line profile;
S2obtaining inlet and outlet sections of the flow channel by taking a perpendicular line of the central flow line, and dividing the central flow line between the inlet and outlet sections of the flow channel into n sections;
S3making vertical lines of the central flow line on the dividing points of the two adjacent sections, and respectively taking points on the vertical lines and on the two sides of the central flow line, so that the length of a line segment formed by two points taken on one vertical line is equal to the value of the flow area to be achieved at the position;
S4fitting all points below the central flow line to form a suction surface profile, and taking outAnd fitting points above all the central flow lines to form suction surface molded lines.
According to an embodiment of the invention, said step S1The method specifically comprises the following steps: and selecting a first mean camber line, moving a grid distance downwards to obtain a second mean camber line of the adjacent blade, and moving the first mean camber line downwards by half grid distance to obtain the central streamline of the flow channel formed by the adjacent blade.
According to an embodiment of the invention, said step S2The method specifically comprises the following steps: the incoming flow direction of the airflow is sequentially made into a series of vertical lines of the central flow line at certain intervals, a first vertical line is defined as a flow channel inlet section, and the flow channel inlet section passes through the front edge point of the first mean camber line and is intersected with the second mean camber line.
According to an embodiment of the invention, said step S2The method specifically comprises the following steps: make a series in proper order by the direction of the effluence of air current with a determining deviation the perpendicular line of central streamline, will be first perpendicular line definition runner exit cross-section, runner exit cross-section pass the trailing edge point of second mean camber line and with first mean camber line is crossing.
According to an embodiment of the invention, said step S2The method specifically comprises the following steps: taking a point E on the flow channel inlet cross-section such that the length of the line from the leading edge point of the first mean camber line to the point E is equal to the reading of the flow area at the flow channel inlet of the central flow line;
taking a point F on the flow passage outlet cross section, and enabling the length of the line from the tail edge point of the second mean camber line to the point F to be equal to the reading of the flow area at the flow passage outlet of the central flow line.
According to an embodiment of the invention, said step S2The method specifically comprises the following steps: taking a leading edge point and a trailing edge point of the central flow line as a head-tail end point, and dividing the head-tail end point into n sections according to the length, wherein n is more than or equal to 2;
the front edge point of the central flow line is the intersection point of the central flow line and the inlet section of the flow channel, and the tail edge point of the central flow line is the intersection point of the central flow line and the outlet section of the flow channel.
According to an embodiment of the invention, said step S3The method specifically comprises the following steps: and respectively marking the dividing points of each section on the central streamline as H1, H2 and H3 … Hn, and respectively taking each dividing point as a vertical line of the central streamline.
According to an embodiment of the invention, said step S3The method specifically comprises the following steps: for each demarcation point, calculating a dimensionless length of the demarcation point on a line segment between a leading edge point and a trailing edge point of the central flow line;
and searching the corresponding through flow area according to the dimensionless length value corresponding to the dividing point, and searching two points on the corresponding vertical line, so that the length of the line between the two points is equal to the dimensionless length value corresponding to the dividing point, and the corresponding through flow area is searched.
According to an embodiment of the invention, said step S4The method specifically comprises the following steps: connecting the leading edge point of the second mean camber line with the point E on the inlet section of the runner by adopting a curve;
fitting said point E, a point taken on said vertical line, and a trailing edge point of said second mean camber line such that a curve on said second mean camber line between a point forward of said flowpath inlet cross-section to said point E and a curve between said point E to said trailing edge point of said second mean camber line continue at least two times at said point E to form a blade suction surface profile;
connecting the trailing edge point of the first mean camber line with the point F on the section of the flow passage outlet by adopting a curve;
fitting said point F, a point taken on said vertical line, and a leading edge point of said first mean camber line such that a curve on said first mean camber line between a point located aft of said flowpath exit cross-section to said point F and a curve between said point F to a trailing edge point of said first mean camber line continue at least two times at said point F to form a blade pressure surface profile.
According to an embodiment of the invention, said step S4Further comprising: and translating the suction surface profile of the blade upwards by a grid pitch to form a complete elementary blade profile.
The positive progress effects of the invention are as follows:
the modeling method of the axial flow compressor element blade profile can use the distribution rule of the flow area as modeling input, and designs the compressor blade profile meeting the requirement of the pre-specified distribution rule of the flow area in a forward and direct mode, thereby realizing the flow velocity distribution or shock wave structure and the like which are required to be achieved.
Drawings
The above and other features, properties and advantages of the present invention will become more apparent from the following description of the embodiments with reference to the accompanying drawings in which like reference numerals denote like features throughout the several views, wherein:
FIG. 1 is a diagram illustrating a three-dimensional CFD calculation.
FIG. 2 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention1Schematic representation of (a).
FIG. 3 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention2Schematic representation of (a).
FIG. 4 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention3Is shown schematically in figure one.
FIG. 5 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention3Schematic diagram two.
FIG. 6 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention3Schematic diagram three of (a).
FIG. 7 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention4Schematic representation of (a).
[ reference numerals ]
First mean camber line 10
One grid pitch a
Second mean camber line 20
Leading edge point A of the first mean camber line
Flow channel inlet cross section 41
Leading edge point B of the center flow line
Flow channel outlet cross section 51
Trailing edge point C of second mean camber line
Trailing edge point D of the center flow line
Detailed Description
In order to make the aforementioned objects, features and advantages of the present invention comprehensible, embodiments accompanied with figures are described in detail below.
Embodiments of the present invention will now be described in detail with reference to the accompanying drawings. Reference will now be made in detail to the preferred embodiments of the present invention, examples of which are illustrated in the accompanying drawings. Wherever possible, the same reference numbers will be used throughout the drawings to refer to the same or like parts.
Further, although the terms used in the present invention are selected from publicly known and used terms, some of the terms mentioned in the description of the present invention may be selected by the applicant at his or her discretion, the detailed meanings of which are described in relevant parts of the description herein.
Furthermore, it is required that the present invention is understood, not simply by the actual terms used but by the meaning of each term lying within.
FIG. 2 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention1Schematic representation of (a). FIG. 3 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention2Schematic representation of (a). FIG. 4 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention3Is shown schematically in figure one. FIG. 5 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention3Schematic diagram two. FIG. 6 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention3Schematic diagram three of (a). FIG. 7 shows the step S of the blade profile modeling method for axial flow compressor element of the present invention4Schematic representation of (a).
As shown in fig. 2 to 7, the invention discloses a method for modeling a basic blade profile of an axial flow compressor, which comprises the following steps:
step S1And obtaining the central streamline of the flow passage enclosed by the adjacent blades according to the camber line profile.
Preferably, as shown in fig. 2, a first mean camber line 10 is selected, a pitch a is shifted downward to obtain a second mean camber line 20 of the adjacent blade, and the first mean camber line 10 is shifted downward by a half pitch a/2 to obtain a center streamline 30 of the flow channel formed by the adjacent blade.
Step S2And the inlet and outlet sections of the flow channel are obtained by taking a perpendicular line of the central flow line, and the central flow line between the inlet and outlet sections of the flow channel is divided into n sections.
Preferably, as shown in fig. 3, the left airflow inflow direction in the drawing is denoted as LE side (Leading Edge), and the right airflow outflow direction in the drawing is denoted as TE side (Trailing Edge). Starting from the incoming flow direction (LE side) of the gas flow, a series of perpendicular lines 40 of the center flow line 30 are made in sequence at intervals until there is a first perpendicular line passing through the leading edge point a of the first mean camber line 10 and intersecting the second mean camber line 20. I.e. the first perpendicular is defined as the channel entry section 41, the channel entry section 41 passing through the leading edge point a of the first mean camber line 10 and intersecting the second mean camber line 20. The intersection point of the flow channel inlet section 41 and the central flow line 30 is taken as a leading edge point B of the central flow line, and the leading edge point B corresponds to the position with the abscissa of 0 in fig. 1.
Similarly, as shown in fig. 3, a series of perpendicular lines 50 of the center flow line 30 are sequentially formed at regular intervals from the outflow direction (TE side) of the gas flow, and the first perpendicular line is directed to exist through the trailing edge point C of the second mean camber line 20 and intersect the first mean camber line 10. I.e. the first perpendicular line, is defined as the flow path exit cross-section 51, the flow path exit cross-section 51 passing through the trailing edge point C of the second mean camber line 20 and intersecting the first mean camber line 10. The intersection of the flow channel exit section 51 and the central flow line 30 is taken as the trailing edge point D of the central flow line 30, which corresponds to the position on the abscissa 1 in fig. 1.
Then, as shown in fig. 4, a point E is taken on the flow path inlet section 41 so that the length of the line from the leading edge point a of the first camber line 10 to the point E (i.e., AE line segment) is equal to the reading of the flow area at the flow path inlet of the center flow line 30, i.e., the AE line segment length b is equal to the reading of the ordinate (representing the flow area) when the abscissa is 0 in fig. 1.
Meanwhile, as shown in fig. 4, a point F is taken on the flow passage outlet section 51 so that the length of the line from the trailing point C of the second camber line 20 to the point F (i.e., the CF line segment) is equal to the reading of the flow area at the flow passage outlet of the central streamline 30, i.e., so that the CF line segment length C is equal to the reading of the ordinate (representing the flow area) when the abscissa is 1 in fig. 1.
Then, as shown in FIG. 5, the curve BD is divided into n segments according to the length by using the leading edge point B and the trailing edge point D of the central flow line 30 as the head and tail end points, where n is greater than or equal to 2. As shown in fig. 5, in this embodiment, 4 segments are taken as an example, and may be divided equally or unequally according to a certain rule. Here, the leading edge point B of the central streamline 30 is the intersection of the central streamline 30 and the runner inlet section 41, and the trailing edge point D of the central streamline 30 is the intersection of the central streamline 30 and the runner outlet section 51.
Step S3And making vertical lines of the central flow line on the dividing points of the two adjacent sections, and respectively taking points on the vertical lines and on the two sides of the central flow line, so that the length of a line segment formed by two points taken on one vertical line is equal to the value of the flow area to be achieved at the position.
Preferably, as shown in FIG. 5, the demarcation points of each segment on the center flow line 30 are respectively marked as H1, H2, H3 … Hn, and each demarcation point is a perpendicular line which is perpendicular to the center flow line 30 and is marked as 31, 32, 33 ….
As shown in FIG. 6, for each of the demarcation points, its dimensionless length on the line segment (i.e., curved segment BD) between the leading edge point B and the trailing edge point D of the central flow line 30 is calculated.
And searching the corresponding through flow area according to the dimensionless length value corresponding to the dividing point, and searching two points on the corresponding vertical line, so that the length of the line between the two points is equal to the dimensionless length value corresponding to the dividing point, and the corresponding through flow area is searched.
More specifically, the dimensionless length of the dividing point on the curve segment BD is calculated in the following manner: BH1 curve length/BD curve length.
The flow Area1 corresponding to the point is obtained by searching in fig. 1 according to the calculated dimensionless length value of the point H1 or calculating according to a functional relation Area (f) (l) corresponding to the curve, and a point H11 and a point H12 are taken on the perpendicular line 31 (as shown in fig. 6), so that the length of the segment H11H12 is equal to that of the Area 1.
Here, the coefficient k1 is defined as: H1H12 line segment length/Area 1, the value range of k1 is specified as: 0 < k1 < 1. Similarly, for points H2 and H3, points … and line segments 32 and 33, 33 …, a series of points H21, H22, H31, H32 … and corresponding coefficients k2 and k3 … are obtained by processing in the same way.
Step S4And fitting the points below all the taken central flow lines to form suction surface molded lines, and fitting the points above all the taken central flow lines to form suction surface molded lines.
As shown in fig. 7, the leading edge point a ' of the second mean camber line 20 is connected to a point E on the inlet cross-section 41 of the flow channel by a curve (where the leading edge point a ' of the second mean camber line 20 is a point corresponding to the leading edge point a of the first mean camber line 10 after being shifted), i.e., an a ' E curve, and the curve can be obtained by a design method of a straight-line inlet blade profile, a pre-compressed blade profile, a customized blade profile, etc., where no special requirement is made on the design method of the section profile.
The point E, the point taken on the perpendicular line and the trailing edge point C of the second mean camber line 20 are fitted such that the curve from the point a 'on the second mean camber line 20 before the channel entrance section 41 to the point E and the curve from the point E to the trailing edge point C of the second mean camber line 20 continue at least two times at the point E to form a blade suction surface profile line a' C.
Specifically, the points E, H11, H21, and H31 … C are fitted using a mathematical tool such as a polynomial, a bezier curve, or a B-spline. The A' E curve and the EC curve are guaranteed to be continuous at least second order at the point E. Thereby forming the blade suction profile line a' C curve.
Similarly, the trailing edge point C ' of the first mean camber line 10 is connected to the point F on the flow channel outlet cross-section 51 by a curve (here, the leading edge point C ' of the first mean camber line 10 is the point corresponding to the shifted trailing edge point C of the second mean camber line 20), i.e., a curve FC '.
The point F, the point taken on the vertical line and the leading edge point a of the first mean camber line 10 are fitted such that the curve from the leading edge point a of the first mean camber line 10 to the point F and the curve from the point F to the point C' of the first mean camber line 10 located behind the flow channel outlet cross-section 51 continue at the point F at least second order forming a blade pressure surface profile.
Specifically, the points A, H12, H22, and H32 … F are fitted using a mathematical tool such as a polynomial, a bezier curve, or a B-spline. The AF curve and FC' curve are guaranteed to be at least second order continuous at point F. Thereby forming a vane pressure profile AC' curve.
And finally, translating the blade suction surface molded line A' C upwards by a grid pitch a to form a complete elementary blade profile. Thus, the modeling work can be completed.
According to the description of the method, the design input of the element blade profile modeling method of the axial flow compressor at least comprises the profile camber line, the grid pitch and the distribution rule of the flow area. The first mean camber line may be defined by a double circular arc, a multiple circular arc, a free mean camber line, or any other means that can be used to define a mean camber line, which is not particularly required in the present invention. The pitch a is generally defined in the subject as the circumferential spacing between two adjacent rows of blades. The distribution rule of the flow area is shown in fig. 1, and is a functional relation formula with the dimensionless length of the central flow line as an independent variable and the flow area as a dependent variable.
Of course, it should be noted here that fig. 1 only shows an example of a flow area distribution rule, and it is not meant to limit the modeling method of the present invention to the area distribution rule, and the flow area distribution rule in the actual modeling process is determined according to the actual requirement.
In summary, the key of the element blade profile modeling method of the axial flow compressor is to move the camber line by one grid pitch to form the camber line of the adjacent blade and move by half grid pitch to form the central flow line. The inlet and outlet cross sections of the flow channel are determined by taking a vertical line on a central flow line. Then, the central flow line between the inlet and the outlet is equally or unequally divided into n sections, a perpendicular line is drawn at the dividing point of each section, and a preassigned flow area distribution rule is realized by taking points on the perpendicular line.
The modeling method of the axial flow compressor element blade profile can use the distribution rule of the flow area as modeling input, and designs the compressor blade profile meeting the requirement of the pre-specified distribution rule of the flow area in a forward and direct mode, thereby realizing the flow velocity distribution or shock wave structure and the like which are required to be achieved.
While specific embodiments of the invention have been described above, it will be appreciated by those skilled in the art that these are by way of example only, and that the scope of the invention is defined by the appended claims. Various changes and modifications to these embodiments may be made by those skilled in the art without departing from the spirit and scope of the invention, and these changes and modifications are within the scope of the invention.
Claims (10)
1. The modeling method of the blade profile of the axial flow compressor element is characterized by comprising the following steps of:
S1obtaining a central streamline of a flow passage enclosed by the adjacent blades according to the camber line profile;
S2obtaining inlet and outlet sections of the flow channel by taking a perpendicular line of the central flow line, and dividing the central flow line between the inlet and outlet sections of the flow channel into n sections;
S3making vertical lines of the central flow line on the dividing points of the two adjacent sections, and respectively taking points on the vertical lines and on the two sides of the central flow line, so that the length of a line segment formed by two points taken on one vertical line is equal to the value of the flow area to be achieved at the position;
S4and fitting the points below all the taken central flow lines to form suction surface molded lines, and fitting the points above all the taken central flow lines to form suction surface molded lines.
2. Method for shaping the blade profile of an axial compressor element according to claim 1, characterised in that step S is carried out1The method specifically comprises the following steps: selecting a first mean camber line, moving a grid pitch downwards to obtain a second mean camber line of an adjacent blade, and enabling the first mean camber line to be in a first neutral camber lineAnd moving the arc line downwards by half grid distance to obtain the central streamline of the flow channel formed by the adjacent blades.
3. Method for shaping the blade profile of an axial compressor element according to claim 2, characterised in that step S is carried out2The method specifically comprises the following steps: the incoming flow direction of the airflow is sequentially made into a series of vertical lines of the central flow line at certain intervals, a first vertical line is defined as a flow channel inlet section, and the flow channel inlet section passes through the front edge point of the first mean camber line and is intersected with the second mean camber line.
4. Method for shaping the blade profile of an axial compressor element according to claim 3, characterised in that step S consists in2The method specifically comprises the following steps: make a series in proper order by the direction of the effluence of air current with a determining deviation the perpendicular line of central streamline, will be first perpendicular line definition runner exit cross-section, runner exit cross-section pass the trailing edge point of second mean camber line and with first mean camber line is crossing.
5. Method for shaping the blade profile of an axial compressor element according to claim 4, characterised in that step S consists in2The method specifically comprises the following steps: taking a point E on the flow channel inlet cross-section such that the length of the line from the leading edge point of the first mean camber line to the point E is equal to the reading of the flow area at the flow channel inlet of the central flow line;
taking a point F on the flow passage outlet cross section, and enabling the length of the line from the tail edge point of the second mean camber line to the point F to be equal to the reading of the flow area at the flow passage outlet of the central flow line.
6. Method for shaping the blade profile of an axial compressor element according to claim 5, characterised in that step S consists in2The method specifically comprises the following steps: taking a leading edge point and a trailing edge point of the central flow line as a head-tail end point, and dividing the head-tail end point into n sections according to the length, wherein n is more than or equal to 2;
the front edge point of the central flow line is the intersection point of the central flow line and the inlet section of the flow channel, and the tail edge point of the central flow line is the intersection point of the central flow line and the outlet section of the flow channel.
7. Method for shaping the blade profile of an axial compressor element according to claim 6, characterised in that step S consists in3The method specifically comprises the following steps: and respectively marking the dividing points of each section on the central streamline as H1, H2 and H3 … Hn, and respectively taking each dividing point as a vertical line of the central streamline.
8. Method for shaping the blade profile of an axial compressor element according to claim 7, characterised in that step S consists in3The method specifically comprises the following steps: for each demarcation point, calculating a dimensionless length of the demarcation point on a line segment between a leading edge point and a trailing edge point of the central flow line;
and searching the corresponding through flow area according to the dimensionless length value corresponding to the dividing point, and searching two points on the corresponding vertical line, so that the length of the line between the two points is equal to the dimensionless length value corresponding to the dividing point, and the corresponding through flow area is searched.
9. Method for shaping the blade profile of an axial compressor element according to claim 8, characterised in that step S consists in4The method specifically comprises the following steps: connecting the leading edge point of the second mean camber line with the point E on the inlet section of the runner by adopting a curve;
fitting said point E, a point taken on said vertical line, and a trailing edge point of said second mean camber line such that a curve on said second mean camber line between a point forward of said flowpath inlet cross-section to said point E and a curve between said point E to said trailing edge point of said second mean camber line continue at least two times at said point E to form a blade suction surface profile;
connecting the trailing edge point of the first mean camber line with the point F on the section of the flow passage outlet by adopting a curve;
fitting said point F, a point taken on said vertical line, and a leading edge point of said first mean camber line such that a curve on said first mean camber line between a point located aft of said flowpath exit cross-section to said point F and a curve between said point F to a trailing edge point of said first mean camber line continue at least two times at said point F to form a blade pressure surface profile.
10. Method for shaping the blade profile of an axial compressor element according to claim 9, characterised in that step S is carried out4Further comprising: and translating the suction surface profile of the blade upwards by a grid pitch to form a complete elementary blade profile.
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